(4)
Provide electrical power.
(5)
The air data system must have been energized for at least 30 minutes prior to this test.
504
34-17-02 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
C. Test Altitude Alerting System
(1)
Open the following circuit breakers on panel P18:
(a)
ALT ALERT 26V AC
(b)
AIR DATA COMPUTER 115V AC
(c)
AIR DATA COMPUTER 26V AC
(d)
CAPT AUTO XFORMER 115V AC
(e)
CAPT ALTIMETER 26V AC
(f)
AURAL ALERT UNIT 28V DC
(2)
Check that altitude alert controller and captain's altimeter failure warning flags are in view.
(3)
Set the barometric scale setting on the captain's altimeter to 29.92 inches of mercury (or 1013 millibars).
(4)
Close the circuit breakers opened in step (1). Check that flags on altitude alert controller and captain's altimeter are not in view.
(5)
Open ALT ALERT circuit breaker. Check that altitude alert controller flag appears in view.
(6)
Close ALT ALERT circuit breaker. Check that altitude alert controller flag disappears from view.
(7)
Open CAPT ALTIMETER circuit breaker. Check that altitude alert controller and captain's altimeter flags appear in view.
(8)
Close CAPT ALTIMETER circuit breaker. Check that both flags disappear from view.
(9)
Open AIR DATA COMPUTER 115V AC and 26V AC circuit breakers. Check that altitude alert controller and captain's altimeter flags appear in view.
(10)
Close AIR DATA COMPUTER 115V AC and 26V AC circuit breakers. Check that both flags disappear from view.
(11)
Set altitude alert controller to 5000 feet.
(12)
Using the pitot static test set, gradually apply and release vacuum to approach the selected altitude from above. Check that the following occurs:
(a)
At 1000 士70 feet above, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(b)
At 375 士70 feet above, altitude alert indicators go out.
(c)
At 375 士70 feet below, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(d)
At 1000 士70 feet below, altitude alert indicators go out.
(13)
Using the pitot static test set, gradually apply and release vacuum to approach the selected altitude from below. Check that the following occurs:
(a)
At 1000 士70 feet below, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(b)
At 375 士70 feet below, altitude alert indicators go out.
(c)
At 375 士70 feet above, aural alerting unit sounds for 1 to 2 seconds and altitude alert indicators come on.
(d)
At 1000 士70 feet above, altitude alert indicators go out.
(14)
Repeat steps (12) and (13) with altitude alert controller set at altitudes of 10,000, 20,000, and 35,000 feet respectively.
577
Sep 20/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-17-02 Page 503
D. Restore Air Data and Pitot Static System to Normal
(1)
Remove external hoses and static port seals ensuring that no deposit of roughness exists in or about static ports.
(2)
If no longer required, remove electrical power from airplane.
577
34-17-02 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 20/81
PERFORMANCE DATA COMPUTER SYSTEM - DESCRIPTION AND OPERATION
1. General
A. The Performance Data Computer System is a digital computer system designed to improve airplane fuel economy and provide flight guidance data to reduce flight crew workload. Performance advisory data is displayed on the control display unit (CDU), enabling the pilot to investigate essential flight and fuel information for various flight modes and profiles. Decision making information related to specific situations, such as enroute diversions, engine shutdown, and step climbs and descent is also displayed. In addition, the PDC sends thrust, airspeed and altitude information to the automatic flight control system (AFCS) for fuel economy optimization of flight control. A flight index number can be programmed into the PDCS to modify maximum economy flight modes according to how time related costs compare to fuel costs.
B. The PDCS consists of a high speed computer, a control display unit, and two mode
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 導航 NAVIGATION 1(41)
